CN214154122U - Ground redundant power supply system for carrier rocket - Google Patents
Ground redundant power supply system for carrier rocket Download PDFInfo
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- CN214154122U CN214154122U CN202022765533.2U CN202022765533U CN214154122U CN 214154122 U CN214154122 U CN 214154122U CN 202022765533 U CN202022765533 U CN 202022765533U CN 214154122 U CN214154122 U CN 214154122U
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Abstract
The utility model provides a redundant power supply system in carrier rocket ground, include: the power supply system comprises a main power supply module, an auxiliary power supply module, a measurement, emission, control and power supply and distribution module, an arrow load module and a control module; the main power supply module and the auxiliary power supply module are connected to the test, launch and control power supply and distribution module in a hot standby redundancy control mode, and the control module automatically selects the main power supply module or the auxiliary power supply module to supply power to the rocket load module. The redundant power supply system ensures that the system is smoothly operated for measurement, transmission and control, and realizes reliable switching of ground power supply.
Description
Technical Field
The utility model relates to a redundant power supply field, concretely relates to redundant power supply system in carrier rocket ground.
Background
In a launch control system for testing launch of a launch vehicle, an onboard power supply and distribution system is an important component of the launch control system. With the rapid development of the aerospace technology, the aerospace electronic devices are increased day by day, the power consumption is increased continuously, the design of a power supply and distribution system is more complex due to the changes, meanwhile, higher requirements are also provided for the reliability and safety of power supply, and the ground power supply is more prone to accidental faults due to the increase of the power consumption. Once the power supply equipment is powered off, the arrow control system can cause the test flow to be incapable of continuing, the product stops working, and the arrow product is damaged if the power supply equipment is powered off. Particularly, when the launch process of the carrier rocket is carried out, the front end is unattended, if a fault is caused by abnormal ground power supply, an operator needs to go to the site to carry out operations such as emergency investigation and maintenance, and certain potential safety hazards exist.
The conventional power supply and distribution system for measuring, generating and controlling is that a ground power supply supplies power to a system on an arrow, any fault of the power supply in the state can cause the control system to work normally, the requirement on the reliability of a single power supply device is greatly increased, and the fault of the power supply can damage the control system device.
In view of the above, it is desirable to design a redundant power supply system for a launch vehicle ground, which has a redundant power supply and can safely and reliably cut off a faulty power supply.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome prior art not enough, provide a redundant power supply system in carrier rocket ground.
The utility model provides a redundant power supply system in carrier rocket ground, include: the power supply system comprises a main power supply module, an auxiliary power supply module, a measurement, emission, control and power supply and distribution module, an arrow load module and a control module; the main power supply module and the auxiliary power supply module are connected to the test, launch and control power supply and distribution module in a hot standby redundancy control mode, and the control module automatically selects the main power supply module or the auxiliary power supply module to supply power to the rocket load module.
According to the utility model discloses an aspect, survey and send out accuse power supply and distribution module and include: the main power supply voltage regulating module and the rocket upper voltage regulating module are connected with the main power supply voltage regulating module; when the main power supply module supplies power to the rocket load module, the control module controls the main power voltage regulating module and the rocket voltage regulating module to enable voltage on the rocket to be constant.
According to an aspect of the present invention, the power distribution module further comprises: the auxiliary power supply voltage regulating module; when the auxiliary power supply module supplies power to the rocket load module, the control module controls the auxiliary power voltage regulating module and the rocket voltage regulating module to enable voltage on the rocket to be constant.
According to an aspect of the present invention, the control module includes: and the host detection module is configured to detect the working state and the power supply voltage value of the main power supply module in real time.
According to an aspect of the present invention, the control module further comprises: and the auxiliary machine detection module is configured to detect the working state and the power supply voltage value of the auxiliary power supply module in real time.
According to an aspect of the present invention, the control module further comprises: and the load detection module is configured to detect the power supply state of the voltage regulation module on the arrow and the voltage value on the arrow in real time.
According to the utility model discloses an aspect, the main power supply voltage regulation module realizes the pressure regulating through the control of first relay, the common port of first relay with main power supply voltage regulation module connects, the normally closed contact of first relay with main power supply module connects, the normally open contact of first relay with voltage regulation module connects on the arrow.
According to the utility model discloses an aspect, the secondary power supply voltage regulating module realizes the pressure regulating through the control of second relay, the common port of second relay with the secondary power supply voltage regulating module is connected, the normally closed contact of second relay with the secondary power supply module is connected, the normally open contact of second relay with voltage regulating module connects on the arrow.
According to the utility model discloses an aspect, host computer detection module passes through the closed condition judgement of third relay main power supply module's operating condition, the solenoid both ends of third relay respectively with main power supply module's positive negative pole is connected.
According to the utility model discloses an aspect, auxiliary engine detection module passes through the closed condition judgement of fourth relay auxiliary power supply module's operating condition, the solenoid both ends of fourth relay respectively with auxiliary power supply module's positive negative pole is connected.
The utility model discloses a carrier rocket ground redundancy power supply system sets up main power supply module and auxiliary power supply module, and through gathering power operating condition as the switching condition, but safe and reliable's fault power supply that cuts off guarantees that system's survey is sent out accuse operation and is gone on smoothly, realizes the reliable switching of ground power supply.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of the specification of the invention, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.
Fig. 1 is a schematic diagram of a redundant power supply system on the ground for a launch vehicle according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a redundant power supply system on the ground for a launch vehicle according to yet another embodiment of the present invention;
FIG. 3 is a schematic diagram of a launch vehicle ground redundant power supply circuit according to an embodiment of the present invention;
fig. 4 is a schematic diagram of a control module of a ground redundant power supply circuit for a launch vehicle according to an embodiment of the present invention.
Detailed Description
The features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention, for the purposes of illustrating the principles of the invention. Additionally, the components in the drawings are not necessarily to scale. For example, the dimensions of some of the structures or regions in the figures may be exaggerated relative to other structures or regions to help improve understanding of embodiments of the present invention.
The directional terms appearing in the following description are directions shown in the drawings and do not limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as the case may be, by those of ordinary skill in the art.
Furthermore, the terms "comprises," "comprising," "includes," "including," "has," "having" or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a structure or component comprising a list of elements does not include only those elements but may include other mechanical components not expressly listed or inherent to such structure or component. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of additional like elements in the article or device comprising the element.
Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.
Fig. 1 is a schematic diagram of a redundant power supply system on the ground for a launch vehicle according to an embodiment of the present invention; FIG. 2 is a schematic diagram of a redundant power supply system on the ground for a launch vehicle according to yet another embodiment of the present invention; FIG. 3 is a schematic diagram of a launch vehicle ground redundant power supply circuit according to an embodiment of the present invention; fig. 4 is a schematic diagram of a control module of a ground redundant power supply circuit for a launch vehicle according to an embodiment of the present invention.
As shown in fig. 1, the utility model provides a redundant power supply system on carrier rocket ground includes: the power supply system comprises a main power supply module, an auxiliary power supply module, a measurement, emission, control and power supply and distribution module, an arrow load module and a control module; the main power supply module and the auxiliary power supply module are connected to the test, launch and control power supply and distribution module in a hot standby redundancy control mode, and the voltage amplitude of the main power supply module is larger than that of the auxiliary power supply module; the control module automatically selects the main power supply module or the auxiliary power supply module to supply power to the load module on the arrow.
According to the utility model discloses an aspect, host computer detection module judges main power supply module's operating condition through the closed condition of third relay, and the solenoid both ends of third relay are connected with main power supply module's positive negative pole respectively.
According to the utility model discloses an aspect, auxiliary engine detection module judges auxiliary power supply module's operating condition through the closed condition of fourth relay, and the solenoid both ends of fourth relay are connected with auxiliary power supply module's positive negative pole respectively.
Specifically, as shown in fig. 3, in this embodiment, the main power supply module is connected to the measurement, emission and control power supply and distribution module, and the main power supply module converts the mains voltage into a power supply voltage required by the rocket load module, so as to supply power to the measurement, emission and control power supply and distribution module. The output of the main power supply module is connected in series to a power supply and distribution bus of the test and control system through a diode V1, the positive power supply output of the main power supply module is connected to a third relay K3 coil, the other end of the third relay K3 coil is connected to the negative of the main power supply module, and the output state of the main power supply module is monitored in real time through the contact closing state of the third relay K3.
The auxiliary power supply module is connected with the power supply and distribution circuit for measurement and control, converts the mains supply voltage into the power supply voltage required by the load module on the rocket, and supplies power for the power supply and distribution module for measurement and control. The output of the auxiliary power supply module is connected in series to a power distribution bus for measurement, emission and control through a diode V2, the positive power supply output of the auxiliary power supply module is connected to a fourth relay K4 coil, the other end of the fourth relay K4 coil is connected to the negative of the auxiliary power supply module, and the output state of the auxiliary power supply module is monitored in real time through the contact closing state of the fourth relay K4.
The main power supply module is connected with the power supply and distribution module for measurement and control, the main power supply module converts mains voltage into power supply voltage required by the load module on the rocket and outputs the power supply voltage to a bus of the power supply and distribution module for measurement and control, the auxiliary power supply module is connected with the power supply and distribution circuit for measurement and control, the auxiliary power supply module converts the mains voltage into the power supply voltage required by the load module on the rocket and outputs the power supply voltage to the bus of the power supply and distribution module for measurement and control, and the voltage amplitude of the main power supply module is larger than that of the auxiliary power supply module.
The rocket load module is connected with the power supply and distribution measuring and controlling module, the rocket load module is connected with the sixth relay K6 and the seventh relay K7 in series right above the power supply and distribution measuring and controlling bus, and the coils of the sixth relay K6 and the seventh relay K7 are controlled by the control module. And the load module on the arrow is directly connected with the power supply and distribution bus load and the power distribution bus load.
The ground redundant power supply system of the carrier rocket can greatly reduce the reliability of a single ground power supply product, the existing commercial power supply can meet the requirement of the system reliability, the cost of a test, launch and control system is greatly reduced, and the complexity of a single machine is reduced.
As shown in fig. 2, according to an aspect of the present invention, the power supply and distribution module includes: the main power supply voltage regulating module and the rocket upper voltage regulating module are connected with the main power supply voltage regulating module; when the main power supply module supplies power to the rocket load module, the control module controls the main power voltage regulating module and the rocket voltage regulating module to enable voltage on the rocket to be constant.
According to the utility model discloses an aspect, the main power supply voltage regulation module realizes the pressure regulating through the control of first relay, and the common port and the main power supply voltage regulation module of first relay are connected, and the normally closed contact of first relay is connected with main power supply module, and the normally open contact of first relay is connected with voltage regulation module on the arrow.
Specifically, when the main power supply module supplies power to the arrow load module, the control module controls the main power supply voltage regulating module and the arrow voltage regulating module to enable the voltage on the arrow to be constant, the main power supply voltage regulating module is connected with the common end of the first relay K1, the normally closed contact of the first relay K1 is connected with the output of the main power supply module, and the normally open contact of the first relay K1 is connected with the arrow voltage regulating module. The IO5 of the control module controls the working state of the coil of the first relay K1.
According to the utility model discloses an aspect, survey and send out accuse power supply and distribution module and still include: the auxiliary power supply voltage regulating module; when the auxiliary power supply module supplies power to the rocket load module, the control module controls the auxiliary power supply voltage regulating module and the rocket voltage regulating module to enable voltage on the rocket to be constant.
According to the utility model discloses an aspect, the secondary power supply voltage regulating module realizes the pressure regulating through the control of second relay, and the common port and the secondary power supply voltage regulating module of second relay are connected, and the normally closed contact and the secondary power supply power module of second relay are connected, and the normally open contact and the arrow of second relay are connected with voltage regulating module.
Specifically, when the auxiliary power supply module supplies power to the arrow load module, the control module controls the auxiliary power supply voltage regulating module and the arrow voltage regulating module to enable the voltage on the arrow to be constant, the auxiliary power supply voltage regulating module is connected with the public end of the second relay K2, the normally closed contact of the second relay K2 is connected with the output of the auxiliary power supply module, and the normally open contact of the second relay K2 is connected with the arrow voltage regulating module. The IO4 of the control module controls the working state of the coil of the second relay K2.
According to an aspect of the utility model, control module includes: and the host detection module is configured to detect the working state and the power supply voltage value of the main power supply module in real time. Wherein, the main power supply module supply voltage is monitored by the AD2 of the control module.
According to an aspect of the utility model, control module still includes: and the auxiliary machine detection module is configured to detect the working state and the power supply voltage value of the auxiliary power supply module in real time. The power supply voltage of the auxiliary power supply module is monitored through the AD3 of the control module.
According to an aspect of the utility model, control module still includes: and the load detection module is configured to detect the power supply state of the voltage regulation module on the arrow and the voltage value on the arrow in real time. The voltage between the rocket voltage regulating modules is monitored through the AD1 of the control module, the line packages of the fifth relay K5 are connected between the rocket voltage regulating modules at the same time, the control module can monitor the power supply state of the rocket load module in real time, and the output state of the rocket load module is monitored in real time through the contact closing state of the fifth relay K5.
The system can monitor the running states of a main power supply module and an auxiliary power supply module of two ground power supplies in real time, can acquire the working state of the power supplies as switching conditions, can safely and reliably cut off a fault power supply under the condition that one ground power supply fails, ensures that the system is smoothly tested, launched and controlled, and realizes the reliable switching of the ground power supply. The system can also realize the function of switching the voltage regulating points of the main power supply module or the auxiliary power supply module of the two ground power supplies, and the condition that the power supply voltage of the load on the rocket is consistent with the set value of the main power supply module or the auxiliary power supply module of the power supplies is ensured.
On the other hand, the utility model also provides a redundant power supply method in carrier rocket ground, include: connecting the main power supply module and the auxiliary power supply module to the power supply and distribution testing and controlling module, detecting that the main power supply module and the auxiliary power supply module work normally, and supplying power to the rocket load module by the power supply and distribution testing and controlling module through the power supply and distribution testing and controlling module; if the power supply of the rocket load module is normal, the rocket load module delays for a set time, and controls the main power supply voltage regulating module to be communicated with the rocket load module to regulate the voltage; after the working state of the main power supply module is judged to be abnormal, the main power supply voltage regulating module is controlled to be disconnected from the rocket voltage regulating module, and the auxiliary power supply voltage regulating module is controlled to be connected with the rocket voltage regulating module to regulate the voltage of the rocket load module.
Specifically, the main power supply module and the auxiliary power supply module are connected to a power supply and distribution module for testing, power transmission and control, coils of a third relay K3 and a fourth relay K4 are electrified, contacts of the third relay K3 and the fourth relay K4 are closed, IO1 and IO2 in the control module monitor high level to obtain feedback signals of the main power supply module and the auxiliary power supply module which work well, and meanwhile, the working voltage values of the main power supply module and the auxiliary power supply module can be monitored through AD2 and AD3 in the control module.
When the main power supply module and the auxiliary power supply module work normally, the control module enables the coils of the sixth relay K6 and the seventh relay K7 to be powered through controlling IO6, contacts of the sixth relay K6 and the seventh relay K7 are closed, a power measurement, control and power supply and distribution bus is connected with the rocket load module, the rocket load module is powered, meanwhile, the coil of the fifth relay K5 is powered, the contact of the fifth relay K5 is closed, the control module monitors that an IO3 signal is in a high level, and meanwhile, the control module can monitor that AD1 obtains a rocket voltage value.
If the rocket load module is normally powered, after a period of time, the control module controls IO5 to enable the wire package of the first relay K1 to be powered on, the contact of the first relay K1 is closed, at the moment, the main power supply module is switched to the rocket voltage regulating module from the main power supply module, the main power supply module automatically regulates the voltage, and the voltage value of the rocket load module reaches the voltage value set by the main power supply module.
If the control module judges that the working state of the main power supply module is abnormal through the IO1 or the AD2, the IO5 is controlled to be disconnected, the first relay K1 is powered off, after the first relay K1 is powered off, the main power supply voltage regulating module returns to the end of the main power supply module, then the main power supply module is closed through a network signal, meanwhile, the IO4 is controlled through the control module to be powered on, a wire packet of the second relay K2 is powered on, the auxiliary power supply voltage regulating module is switched to the arrow voltage regulating module through the auxiliary power supply module, and the voltage of the arrow load module reaches the voltage value set by the auxiliary power supply module.
The utility model discloses carrier rocket ground redundancy power supply method can use in rocket power supply and distribution at different levels, and normal operation in the in-service use can the reliable switching control between the effectual realization power.
According to an aspect of the present invention, the method for redundant power supply on the ground of a launch vehicle further comprises: when the rocket load module needs to be powered off, the main power supply voltage regulating module or the auxiliary power supply voltage regulating module is disconnected, and the main power supply module and the auxiliary power supply module are disconnected through the power measurement, emission and control power supply and distribution module.
Specifically, the control module disconnects the IO4 and the IO5, so that the main power supply voltage regulating module or the auxiliary power supply voltage regulating module is switched back to the state of the main power supply module or the auxiliary power supply module, then the control module disconnects the IO6, so that the wire packages of the sixth relay K6 and the seventh relay K7 are powered off, the contacts of the sixth relay K6 and the seventh relay K7 are disconnected, the rocket load module is disconnected from the power supply of the measurement, emission and control power supply and distribution bus, the wire package of the fifth relay K5 is powered off, the IO3 of the control module is changed from a high level to a low level, the auxiliary power supply voltage regulating module and the output of the main power supply module are turned off remotely and sequentially, the IO2 of the control module is changed from a high level to a low level, and the IO1 of the control module is changed from a high level to a low level.
As one embodiment of the utility model, two commercial ground power supplies with the same type and number are used in the ground redundant power supply system of the carrier rocket, wherein the main power supply module sets the output voltage amplitude to be 28.5V, and the auxiliary power supply module sets the output voltage amplitude to be 28V; each power supply receives a remote control signal through the control module to control.
The control module is realized through a PLC (programmable logic controller) and a PXI (peripheral component interconnect extension) device, wherein the PLC comprises a power supply module, a communication module, a switching value input module, a switching value output module and the like and is responsible for functions of starting, state acquisition, logic control and the like of the relay, and the PXI comprises a power supply module, a voltage acquisition module, a communication module and the like and is responsible for functions of voltage signal acquisition and the like on the arrow.
In the PLC program design, the input of a PLC input module corresponds to one path of variable% I in a PLC module, one path of output of a PLC output module corresponds to one path of variable% Q in a program, and in the model, IO1 corresponds to% I0.1, IO2 corresponds to% I0.2, IO3 corresponds to% I0.3, IO4 corresponds to% Q0.1, IO5 corresponds to% Q0.2, and IO6 corresponds to% Q0.3. The arrow load module is switched on to be a control command corresponding program% M0.1, and the main power supply module and the auxiliary power supply module are switched to be a control command corresponding program% M0.2. In the PXI program, AD1, AD2 and AD3 carry out voltage value measurement through an AD board card.
The power supply program flow of the loading module on the arrow is as follows:
after the main power supply module and the auxiliary power supply module supply power, the coils of the relays K3 and K4 are electrified, the contacts K3 and K4 are closed, and the normally open contacts% I0.1 and% I0.2 are switched on. AD2 and AD3 were measured by PXI board cards. The PLC receives a remote on-rocket load module connection command, the% M0.1 signal is connected, the% Q0.3 is connected after the time of TON1 is delayed according to a first stroke sequence of the PLC shown in figure 4, so that K6 and K7 coils are powered on, K6 and K7 relay contacts are closed, a power measurement and control power supply and distribution bus is connected with the on-rocket load module, the on-rocket load module is powered on, meanwhile, the K5 relay coil is powered on, the K5 relay is closed, the control circuit monitors that the% IO.3 signal is connected, and the PXI can monitor AD1 to obtain an on-rocket voltage value. If the rocket is normally powered, after the TON2 is delayed, the PLC outputs the% Q0.2 according to the program in the second line of the graph 4 to enable the K1 wire packet to be powered on, the K1 relay is closed, at the moment, the main power supply module of the main power voltage regulating module is switched to the rocket voltage regulating module, and the voltage is automatically regulated to enable the voltage value of the load on the rocket to reach the voltage value 28.5V set by the main power supply module. And ending the power supply program flow of the load on the arrow.
The main and auxiliary power supply module switching program flow:
when the working abnormal% IO.1 signal of the main power supply module is changed into disconnection from connection or the PXI acquires the AD2 value and sends a main and auxiliary power supply module switching command, the PLC receives the main and auxiliary power supply module switching command% M0.2 signal to be connected, after the TON2 is delayed, the PLC cuts off the% Q0.2 signal according to the second program in the figure 4 to power down the K1 relay, after the K1 relay is powered down, the main power supply voltage regulating module switches off the rocket voltage regulating module, then the fault power supply is switched off through a network signal, meanwhile, the fact that the auxiliary power supply module works normally, the I0.2 signal is switched on, the rocket power supply state is normal, the% I0.3 signal is switched on, after the TON3 is delayed, the PLC outputs the% Q0.1 according to the third program in the figure 4 to enable a K2 wire to be powered on, the ground auxiliary power supply voltage regulating module is switched to the rocket voltage regulating module through the auxiliary power supply module, and the rocket load voltage on the rocket reaches the voltage value 28V set by the auxiliary power supply module. And finishing the program switching process of the main and auxiliary power supply modules.
And (3) power-off program flow of the loading module on the arrow:
after the PLC receives a command of turning off a module in charge of an arrow, a% M0.1 signal is turned off, after the TON2 is delayed, the PLC turns off a% Q0.2 according to a program in a second row of a figure 4 to power down a K1 relay, after the K1 relay is powered down, a main power supply module returns to a main power supply module, after the TON3 is delayed, the PLC turns off the% Q0.3 according to a program in a third row of the figure 4 to power down a K2 relay, after the K2 relay is powered down, an auxiliary power supply module returns to an auxiliary power supply module, after the TON1 is delayed, the PLC turns off the% Q0.3 according to a first stroke of the figure 4 to power down K6 and K7 coils, K6 and K7 relay contacts are turned off, a measurement and control power distribution bus and an arrow load module are turned off, and at the same time, a K5 coil is turned off, the K5 relay is turned off, a control circuit% IO.3 signal is turned off, an AD acquisition voltage on the arrow is monitored to be 0V, then a secondary power supply module is turned off by a network signal, and an IO.2 signal is turned off, and then closing the main power supply module through a network signal, changing the% IO.1 signal from on to off, and ending the power-off process of the rocket load module.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A launch vehicle ground redundant power supply system, comprising:
the power supply system comprises a main power supply module, an auxiliary power supply module, a measurement, emission, control and power supply and distribution module, an arrow load module and a control module;
the main power supply module and the auxiliary power supply module are connected to the test, launch and control power supply and distribution module in a hot standby redundancy control mode, and the control module automatically selects the main power supply module or the auxiliary power supply module to supply power to the rocket load module.
2. The launch vehicle ground redundant power supply system of claim 1, wherein said test, launch and control power supply and distribution module comprises:
the main power supply voltage regulating module and the rocket upper voltage regulating module are connected with the main power supply voltage regulating module;
when the main power supply module supplies power to the rocket load module, the control module controls the main power voltage regulating module and the rocket voltage regulating module to enable voltage on the rocket to be constant.
3. The launch vehicle ground redundant power supply system of claim 2, wherein said test, generation, control, and power distribution module further comprises:
the auxiliary power supply voltage regulating module;
when the auxiliary power supply module supplies power to the rocket load module, the control module controls the auxiliary power voltage regulating module and the rocket voltage regulating module to enable voltage on the rocket to be constant.
4. The launch vehicle ground redundant power supply system of claim 1, wherein said control module comprises:
and the host detection module is configured to detect the working state and the power supply voltage value of the main power supply module in real time.
5. The launch vehicle ground redundant power supply system of claim 1, wherein said control module further comprises:
and the auxiliary machine detection module is configured to detect the working state and the power supply voltage value of the auxiliary power supply module in real time.
6. The launch vehicle ground redundant power supply system of claim 2, wherein said control module further comprises:
and the load detection module is configured to detect the power supply state of the voltage regulation module on the arrow and the voltage value on the arrow in real time.
7. The ground redundant power supply system for a launch vehicle according to claim 2, wherein the main power voltage regulating module realizes voltage regulation under the control of a first relay, a common end of the first relay is connected with the main power voltage regulating module, a normally closed contact of the first relay is connected with the main power supply module, and a normally open contact of the first relay is connected with the voltage regulating module on the launch vehicle.
8. The ground redundant power supply system for a launch vehicle according to claim 3, wherein the secondary power supply voltage regulation module realizes voltage regulation under the control of a second relay, a common end of the second relay is connected with the secondary power supply voltage regulation module, a normally closed contact of the second relay is connected with the secondary power supply module, and a normally open contact of the second relay is connected with the voltage regulation module on the rocket.
9. The ground redundant power supply system for a launch vehicle according to claim 4, wherein the host detection module determines the working state of the main power supply module through the closing state of a third relay, and both ends of a coil of the third relay are respectively connected with the positive electrode and the negative electrode of the main power supply module.
10. The ground redundant power supply system for a launch vehicle according to claim 5, wherein the auxiliary engine detection module determines the working state of the auxiliary power supply module through the closing state of a fourth relay, and two ends of a coil of the fourth relay are respectively connected with the positive electrode and the negative electrode of the auxiliary power supply module.
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| CN113985847A (en) * | 2021-10-28 | 2022-01-28 | 北京宇航系统工程研究所 | Ground measurement and control equipment fast switch adaptation system suitable for polytype rocket |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113985847A (en) * | 2021-10-28 | 2022-01-28 | 北京宇航系统工程研究所 | Ground measurement and control equipment fast switch adaptation system suitable for polytype rocket |
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